Questions tagged [orbital-elements]

Orbital elements are a set of parameters that uniquely identify a specific orbit.

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121 views

How to find eccentric anomaly by mean anomaly?

Wikipedia gives me the equation M = E - e*sinE I have M and need to find E. How to do it?
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Are 3 points on an orbit enough to determine the shape of it in practice?

In a question about determining orbital elements from two points on an orbit, some discussion arouse regarding how many points are actually necessary, since two is not sufficient. Determining a conic ...
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Find the Orbital Inclination given all other Elements and a Position on the Ellipse

I'm in a situation where I need to determine an orbit's inclination. At my disposal I have all of the orbit's other Keplerian elements, and I have the vector of a single point on the ellipse. Is ...
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How would you calculate a Hohmann transfer going towards the sun?

If you were going from a lower orbit to a higher orbit such as a Earth-Mars transfer, you would use the periapsis of the transfer orbit in the vis-viva equation to calculate the delta V. But if you ...
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Right Ascension of the Ascending Node (RAAN) Drift and Correction

This one can be a very short and easy question, but I wanna know the proper answer of them.. Few days ago I got a questions like: "What kind of perturbation(s) can cause drift on RAAN value of a ...
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How is it possible that the windows on the ISS mostly face Earth only? [duplicate]

In this article astronaut Clayton C. Anderson states that on the ISS the windows "mosty face Earth, which means that it is only possible to see the stars at the very edges of the windows, and ...
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Calculating TLE, or satellite orbit elements based on angle information (RA and Dec) at multiple epochs

new here. I am trying to 'determine' orbital elements of a given satellite. Based on TLE from space-track, or CelesTrak, I observed several satellites resulting in 10 to 20 RA and Dec pairs for each ...
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Obtaining position of GPS and GLONASS satellites from RINEX navigation files

I am currently trying to understand the best way to use the available information in RINEX navigation files for GPS and GLONASS satellites. My main goal currently is to calculate the position at epoch ...
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How would you convert keplerian orbital elments into cartesain vectors with quaternions?

Coverting the keplerian elements to cartesain vectors ( posistion and velocity) is relatievly simple by using rotation matrices show in the document here: https://downloads.rene-schwarz.com/download/...
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what range of orbital inclinations will be needed to reach Mars from the Boca Chica launch site?

When SpaceX fly missions out of Boca Chica in South Texas to Mars what orbital inclination will the launch need to be to put the spacecraft on to best transfer orbit to Mars? And will this vary with ...
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Finding the new true anomaly after performing a maneuver

Given a standard set of orbital elements (angular momentum, semi-major axis, eccentricity, inclination, longitude of the ascending node, argument of periapsis, and true anomaly), and a global time ...
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Rotation matrix / coordinate transformation of maneuver parameters from Prograde, Normal, Radial to Cartesian XYZ?

Say I have a state vector and Keplerian elements of an orbiting spacecraft: Position = [x, y, z] Velocity = [vx, vy, vz] Elements = [a, e, i, $\omega$, $\Omega$, $\nu$] And I have the maneuver I ...
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How can I calculate the future position of a satellite orbiting a central body as a function of time using known orbital elements?

Given the position and velocity vectors at one point in an orbit, one can calculate the keplerian elements and thus graph the subsequent orbital path as a circle/ellipse/parabola/hyperbola depending ...
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1answer
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Is there a (low-thrust) thrusting strategy to change a single orbital element alone?

In literature, I have found the optimal thrusting directions (in terms of pitch and yaw) for maximizing changes in each orbital element. These optimal changes, while maximizing one element, have an ...
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What's the lowest periapsis of a successful orbit around the Moon? [duplicate]

What's the lowest periapsis of a successful orbit around the Moon ever made by a moon-orbiting spacecraft? Theoretically, Moon-orbiters can go as low as a foot above the surface due to the lack of an ...
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Is Vallado's Revisiting Spacetrack Report #3 still relevant today?

The title pretty much sums it up. I am reading David A. Vallado's Revisiting Spacetrack Report #3, which was published in 2006 and includes source code for the SGP model series. I was wondering, is ...
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125 views

How can I edit the STK report output?

I have been dealing for a while on a report which is generated by STK. It contains basically time, azimuth, elevation and range data. Besides those data I need to also generate the theta and phi ...
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How much delta-v does it take to go from one arbitrary orbit to another?

This is, in theory, very basic rocket science. I can't seem to find a solution on here though, so I'm asking in the hopes you'll enlighten me and my amateurish ways. I've got a set of Keplerian ...
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2answers
384 views

ISS nodal precession

I was confused by JPL Horizons data showing time variations in the ISS longitude of ascending node, until I realized maybe the orbital plane itself rotates around earth... A quick web search then ...
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How to calculate launch window?

Say I want to launch a rocket in the next 5 days for rendezvous with the ISS. I need to figure out when the orbital plane of the ISS will intersect my launch site---e.g., Kennedy. The orbital plane is ...
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Reasonable argument of periapsis?

My intuition for orbital parameters is still poor, so I'm wondering if someone can tell if my argument of periapsis seems reasonable. I'm simulating a launch from Kennedy (28.1 deg latitude, -80.6 deg ...
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Entering elliptical orbit at periapse

Consider a rocket entering an elliptical orbit from launch. Say you want the rocket to enter exactly at periapse---not a few degrees ahead of it, not a few degrees behind it. Can this be done? I have ...
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Setting argument of perigee at orbital insertion?

I've managed to control for altitude, velocity, eccentricity (via flight path angle), orbital inclination, and longitude of ascending node at orbital insertion. Between them, these parameters uniquely ...
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Perigee location?

Suppose I throw a ball eastward from Kennedy and reduce the earth to a point so that the ball can trace an ellipse around it. Because I threw the ball eastward (no vertical or northern velocity ...
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Can we determine the position of an artificial satellite using Kepler's parameters?

I have read that an orbit is defined by Kepler's parameters, so is it possible to determine an exact position of an artificial satellite using those parameters? Forgive me if this is a redundant ...
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1answer
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Determining the launch period for Hohmann transfer

How do you determine the day of a specific launch? I know there are launch windows but they only refer to the time at which a spacecraft must be launched. For a LEO it is apparently 365 days, but what ...
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Lowest possible lunar orbit and has any spacecraft achieved it?

Because the Moon has no atmosphere a spacecraft can theoretically cruise at a very low orbit. What is the lowest possible lunar orbit and which spacecraft achieved it? Was it the Lunar Module of ...
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How to find/extract the semi-major axis from a TLE with Skyfield?

I have a TLE: 1 33591U 09005A 21024.46740879 .00000049 00000-0 52095-4 0 9997 2 33591 99.1927 41.5349 0014084 172.6670 187.4709 14.12449679616592 And I would like ...
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1answer
147 views

Computing a new TLE following a delta-v impulse?

Is there some code or a library out there that can take orbital elements, add a known delta-v component and then compute a new TLE? I found this one https://apps.dtic.mil/dtic/tr/fulltext/u2/a289281....
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1answer
123 views

Launch azimuth from orbital inclination WRT rotating earth?

The formula for launch azimuth given latitude and target orbital inclination goes like this: $$azm = \sin^{-1} \left(\frac{\cos(inc)}{\cos(lat)}\right)$$ I assume the orbital inclination $inc$ and ...
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How long to reach final orbital inclination?

Consider a rocket launch from Kennedy, latitude 28.5 deg, to a target orbital inclination of 50.6 degrees for rendezvous with the ISS. The launch azimuth for this orbital inclination is roughly 45 deg ...
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Plotting satellite ground track with calculated latitude and longitude at a given moment

I have obtained the Classical Orbital Elements for a satellite on a given epoch, and now I would like to plot them on a 2D map. ...
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Does it count as orbital flight if one reentered the atmosphere due to its drag after about 1 revolution?

Imagine a spacecraft entered an orbit around the Earth whose perigee is low enough into the atmosphere so that it reenters and lands after a revolution, without having to perform a reentry burn. While ...
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What does diiferent colours in orbital path seen in the CRS 21 launch video indicate?

The SpaceX broadcast of Falcon 9 - CRS 21 launch showed the orbital path of the vehicle differently than previous videos. Separate green lines and rectangualar boxes were visible. What additional ...
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How to plot this orbit?

I have these data for some orbits, without any explanation about meaning of each datum: ...
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When sending astronauts to the ISS, how does each spacecraft sense the other? [duplicate]

When spacecraft with astronauts tries to dock with the ISS, are there special sensors in each used to track the other? Does one usually do the detection, tracking and orientation in order to "...
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1answer
268 views

Under what conditions can a non-resonant satellite stay hidden from an observer on the ground?

From the perspective of someone on the ground, a satellite is usually not above the horizon all the time. But can a satellite have such an orbit that it is never above the horizon? Such orbits clearly ...
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1answer
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Calculating specific dates of reaching apses given orbital elements?

Given a specific date and heliocentric orbital elements ($a, e, i, \Omega, \omega$, mean anomaly) of a spacecraft in a heliocentric orbit, how can we calculate when it will reach perihelion and how ...
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Do I have enough info to find the true anomaly of an orbit?

For a personal coding project, I'm trying to model orbits of satellites around the Earth. I take in some values from a user and use them to determine the shape of the orbit. I want to model the ...
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Graph Eccentrity Vector in x and y Component

I have one year eccentricity value (the eccentricity magnitude only). I want to know the eccentricity vector in x and y component, so I use this below equation to get it (credit: Hengian Li): After ...
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1answer
63 views

Is it possible to represent an orbit with just a periapsis position and 2 angular velocities?

I was thinking of how complex the orbital elements are and got to wondering whether you can represent orbits in a more simple way. If you start with an ECI coordinate frame and you know the spherical ...
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1answer
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Direct conversion of Keplerian orbital elements to Equatorial coordinate system

In the context of a computer simulation of satellites that orbit earth, I am looking for a (accurate) method for converting Keplerian orbital elements directly to Equatorial coordinate system. The ...
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Most efficient (computationally) orbit propagation for simplified J2 effects

I am looking into modeling large scale constellation (hundreds of satellites) and there coverage over earth given a defined conical FOV. The simplified process is a user defines: Constellation (...
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1answer
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What is the maximum apogee a Dragon spacecraft can reach?

What is the maximum apogee a Crew Dragon can reach in a highly elliptical orbit (by both the Falcon 9 and the Falcon Heavy)? There is a planned touristic mission in which the current apogee record of ...
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What is the maximum apogee a Space Shuttle could have reached?

What is the maximum apogee a Space Shuttle (and which one of the five space-flying Shuttles?) ever reached and what is the maximum one it could have reached? A Space Shuttle never exceeded the apogee ...
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Were/Are the Space Shuttle or the Falcon 9 Dragon capable of achieving an elliptical orbit on whose apogee you'd see the entire Earth?

Was the Space Shuttle and is the Crew Dragon capable of achieving a highly elliptical orbit on whose apogee you could see the entire planet Earth? There will be a touristic flight soon in which an ...
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Keplerian to cartesian elements issue

I am trying to convert between keplerian orbital elements to cartesian position and velocity but something is going wrong. The issue is that I (as a check) compute some keplerian orbital elements with ...
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Compute eccentricity and angular momentum vectors of a binary

I having some trouble finding the direction vectors (in 3D) of the eccentricity and angular momentum of a binary. The issue is that the binary has only been described in Keplerian orbital elements and ...
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2answers
548 views

Visualising orbits from different viewpoints in Python

I have a python program that I use to visualise a planetary orbital system. I convert the orbits to xyz coordinates and then have a basic orrery that views the system from 'above', by simply plotting ...
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Interplanetary space mission debris orbits

I was wondering if anyone knew about a database of orbits for debris from previous interplanetary space missions. I am referring to debris or expired missions by NASA, ESA, JAXA, etc. I know there are ...